18862 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 

system, there is not a direct mechanical 

link between the airplane flight control 

surface and the pilot’s cockpit control 

device as there is on more conventional 

airplanes. Instead, a flight control 

computer commands the airplane flight 

control surfaces, based on input 

received from the cockpit control 

device. The pilot input is modified by 

the flight control computer—based on 

the current airplane flight parameters—

before the command is given to the 

flight control surface. 

Discussion 

The formulation of airplane design 

load conditions in 14 CFR part 25 is 

based on the assumption that the 

airplane is equipped with a control 

system in which there is a direct 

mechanical linkage between the pilot’s 

cockpit control and the control surface. 

Thus, for roll maneuvers, the regulation 

specifies a displacement for the aileron 

itself and does not envision any 

modification of the pilot’s control input. 

Since such a system will affect the 

airplane flight loads and thus the 

structural strength of the airplane, 

special conditions appropriate for this 

type of control system are needed. 

In particular, the special condition 

adjusts the design roll maneuver 

requirements specified in § 25.349(a), so 

that they take into account the effect of 

the Falcon 7X’s electronic flight control 

computer on the control surface 

deflection. The special condition 

requires that the roll maneuver be 

performed by deflection of the cockpit 

roll control, as opposed to specifying a 

deflection of the aileron itself as the 

current regulation does. The deflection 

of the control surface would then be 

determined from the cockpit input, 

based on the computer’s flight control 

laws and the current airplane flight 

parameters. 

Applicability 

As discussed above, these special 

conditions are applicable to the Dassault 

Aviation Model Falcon 7X. Should 

Dassault Aviation apply at a later date 

for a change to the type certificate to 

include another model incorporating the 

same novel or unusual design feature, 

the special conditions would apply to 

that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features of the 

Dassault Aviation Model Falcon 7X of 

airplane. It is not a rule of general 

applicability. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

public comment would result in a 

significant change from the substance 

contained herein. Therefore, because a 

delay would significantly affect the 

certification of the airplane, which is 

imminent, the FAA has determined that 

prior public notice and comment are 

unnecessary and impracticable and that 

good cause exists for adopting these 

special conditions upon issuance. The 

FAA is requesting comments to allow 

interested persons to submit views that 

may not have been submitted in 

response to the prior opportunities for 

comment described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

■ The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for Dassault Aviation Model 

Falcon 7X airplanes. 

Design Roll Maneuvering Conditions 

In lieu of compliance with 14 CFR 

25.349(a), the following special 

conditions apply: 

Maneuvering: The following 

conditions, speeds and cockpit roll 

control motions (except as the motions 

may be limited by pilot effort) must be 

considered in combination with an 

airplane load factor of zero and the twothirds of limit positive maneuvering 

load factor. In determining the resulting 

control surface deflections, the torsional 

flexibility of the wing must be 

considered in accordance with 14 CFR 

25.301(b): 

(1) Conditions corresponding to 

maximum steady rolling velocities and 

conditions corresponding to maximum 

angular accelerations must be 

investigated. For the angular 

acceleration conditions, zero rolling 

velocity may be assumed in the absence 

of a rational time history investigation 

of the maneuver. 

(2) At VA, movement of the cockpit 

roll control up to the limit is assumed. 

The position of the cockpit roll control 

must be maintained until a steady roll 

rate is achieved and then must be 

returned suddenly to the neutral 

position. 

(3) At VC, the cockpit roll control 

must be moved suddenly and 

maintained so as to achieve a roll rate 

not less than that obtained in subparagraph (2) of this paragraph. 

(4) At VD, the cockpit roll control 

must be moved suddenly and 

maintained so as to achieve a roll rate 

not less than one third of that obtained 

in sub-paragraph (2) of this paragraph. 

Issued in Renton, Washington, on April 4, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 07–1809 Filed 4–13–07; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27824; Directorate 

Identifier 2003–NE–12–AD; Amendment 39–

15026; AD 2006–11–05R1] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD) for 

Rolls-Royce plc (RR) RB211–22B series, 

RB211–524B, –524C2, –524D4, –524G2, 

–524G3, and –524H series, and RB211–

535C and –535E series turbofan engines 

with high pressure compressor (HPC) 

stage 3 disc assemblies, part numbers 

(P/Ns) LK46210, LK58278, LK67634, 

LK76036, UL11706, UL15358, UL22577, 

UL22578, and UL24738 installed. That 

AD currently requires removing from 

service certain disc assemblies before 

they reach their full published life if not 

modified with anticorrosion protection. 

This AD requires the same actions but 

relaxes the removal compliance time for 

certain disc assemblies that have a 

record of detailed inspection. This AD 

results from the FAA allowing certain 

affected disc assemblies that entered 

into service before 1990 that have a 

record of detailed inspections, to remain 

in service for a longer period than the 

previous AD allowed. We are issuing 

this AD to relax the compliance time for 

certain disc assemblies and track the 

disc life based on a detailed inspection 

rather than by its entry into service date, 

while continuing to prevent corrosioninduced uncontained disc assembly 

failure, resulting in damage to the 

airplane. 


cprice-sewell on PROD1PC66 with RULES
Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 18863 

DATES: Effective May 1, 2007. The 

Director of the Federal Register 

previously approved the incorporation 

by reference of certain publications 

listed in the regulations as of February 

24, 2004 (69 FR 2661, January 20, 2004). 

We must receive any comments on 

this AD by June 15, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Rolls-Royce plc, P.O. Box 31, 

Derby, England, DE248BJ; telephone: 

011–44–1332–242424; fax: 011–44–

1332–245–418, for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park; Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; telephone 

(781) 238–7178; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: On May 

15, 2006, the FAA issued AD 2006–11–

05, Amendment 39–14609 (71 FR 

29586, May 23, 2006). We also issued a 

correction to that AD on September 26, 

2006 (71 FR 58254, October 3, 2006). 

That AD requires removing from service 

certain disc assemblies before they 

reach their full published life if not 

modified with anticorrosion protection. 

That AD was the result of the 

manufacturer’s reassessment of the 

corrosion risk on HPC stage 3 disc 

assemblies that have not yet been 

modified with sufficient application of 

anticorrosion protection. That 

condition, if not corrected, could result 

in corrosion-induced uncontained disc 

assembly failure, resulting in damage to 

the airplane. 

Actions Since AD 2006–11–05 Was 

Issued 

Since AD 2006–11–05 was issued, RR 

revised an applicable mandatory service 

bulletin (MSB). That MSB allows 

affected disc assemblies that entered 

into service before 1990 that have a 

record of detailed inspections, to remain 

in service for 17 years from last 

overhaul inspection date. But the discs 

are not to exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. We are issuing 

this AD to relax the compliance time for 

certain disc assemblies and track the 

disk life based on a detailed inspection 

rather than by its entry into service date, 

while continuing to prevent corrosioninduced uncontained disc assembly 

failure, resulting in damage to the 

airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of RR MSB No. 

RB.211–72–9661, Revision 5, dated 

December 22, 2006. That MSB allows 

affected disc assemblies that entered 

into service before 1990; and that have 

a record of detailed inspection: 

• To remain in service for 17 years 

from last overhaul inspection date; but 

• Not to exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

We do not incorporate by reference 

this MSB, but we list it under related 

information. 

Bilateral Airworthiness Agreement 

This engine model is manufactured in 

the United Kingdom (UK), and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Under this bilateral 

airworthiness agreement, the CAA, 

which is the airworthiness authority for 

the UK, has kept the FAA informed of 

the situation described above. We have 

examined the findings of the CAA, 

reviewed all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other (RR) RB211–22B series, 

RB211–524B, –524C2, –524D4, –524G2, 

–524G3, and –524H series, and RB211–

535C and –535E series turbofan engines 

of the same type design. We are issuing 

this AD to relax the compliance time for 

certain disc assemblies and to prevent 

corrosion-induced uncontained disc 

assembly failure, resulting in damage to 

the airplane. This AD requires the 

following for affected HPC stage 3 rotor 

disc assemblies: 

• Removing affected disc assemblies 

from service; and 

• Re-machining, inspecting, and 

applying anticorrosion protection; and 

• Re-marking, and returning disc 

assemblies into service; and 

• Allowing affected disc assemblies 

that entered into service before 1990 

that have a record of detailed 

inspection, to remain in service for 17 

years from last overhaul inspection date 

but not to exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

You must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable. Good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2007–27824; Directorate Identifier 

2003–NE–12–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the DMS Web site, 

anyone can find and read the comments 

in any of our dockets. This includes the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 


cprice-sewell on PROD1PC66 with RULES
18864 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Docket Number Change 

We are transferring the docket for this 

AD to the Docket Management System 

as part of our on-going docket 

management consolidation efforts. The 

new Docket No. is FAA–2007–27824. 

The old Docket No. became the 

Directorate Identifier, which is 2003–

NE–12–AD. This AD might get logged 

into the DMS docket, ahead of the 

previously collected documents from 

the old docket file, as we are in the 

process of sending those items to the 

DMS. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (14 

CFR part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–14609 (71 FR 

29586, May 23, 2006) and by adding a 

new airworthiness directive, 

Amendment 39–15026, to read as 

follows: 

2006–11–05R1 Rolls-Royce plc: 

Amendment 39–15026. Docket No. 

FAA–2007–27824; Directorate Identifier 

2003–NE–12–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 1, 2007. 

Affected ADs 

(b) This AD revises AD 2006–11–05, 

Amendment 39–14609. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

RB211–22B series, RB211–524B, –524C2, 

–524D4, –524G2, –524G3, and –524H series, 

and RB211–535C and –535E series turbofan 

engines with high pressure compressor (HPC) 

stage 3 disc assemblies, part numbers (P/Ns) 

LK46210, LK58278, LK67634, LK76036, 

UL11706, UL15358, UL22577, UL22578, and 

UL24738 installed. These engines are 

installed on, but not limited to, Boeing 747, 

Boeing 757, Boeing 767, Lockheed L–1011, 

and Tupolev Tu204 series airplanes. 

Unsafe Condition 

(d) This AD results from the FAA allowing 

certain affected disc assemblies that entered 

into service before 1990 that have a record of 

detailed inspections, to remain in service for 

a longer period than the previous AD 

allowed. We are issuing this AD to relax the 

compliance time for certain disc assemblies 

and track the disc life based on a detailed 

inspection rather than by its entry into 

service date, while continuing to prevent 

corrosion-induced uncontained disc 

assembly failure, resulting in damage to the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Removal of HPC Stage 3 Disc Assemblies 

(f) Remove from service affected HPC stage 

3 disc assemblies identified in the following 

Table 1, using one of the following criteria: 

TABLE 1.—AFFECTED HPC STAGE 3 DISC ASSEMBLIES

Engine model 

Rework band for 

cyclic life accumulated on disc assemblies P/Ns 

LK46210 and 

LK58278 (Pre RR 

Service Bulletin 

(SB) No. RB.211–

72–5420) 

Rework band for 

cyclic life accumulated on disc assembly P/N 

LK67634 (pre RR 

SB No. RB.211–

72–5420) 

Rework band for 

cyclic life accumulated on P/Ns 

LK76036, 

UL11706, 

UL15358, 

UL22577, 

UL22578, and 

UL24738 disc assemblies (pre RR 

SB No. RB.211–

72–9434) 

–22B series ................................................................................................................ 4,000–6,200 7,000–10,000 11,500–14,000 

–535E4 series ............................................................................................................ N/A N/A 9,000–15,000 

–524B–02, B–B–02, B3–02, and B4 series, Pre and Post accomplishment of SB 

No. 72–7730 ........................................................................................................... 4,000–6,000 7,000–9,000 11,500–14,000 

–524B2 and C2 series, Pre SB No. 72–7730 ........................................................... 4,000–6,000 7,000–9,000 11,500–14,000 


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Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 18865 

TABLE 1.—AFFECTED HPC STAGE 3 DISC ASSEMBLIES—Continued 

Engine model 

Rework band for 

cyclic life accumulated on disc assemblies P/Ns 

LK46210 and 

LK58278 (Pre RR 

Service Bulletin 

(SB) No. RB.211–

72–5420) 

Rework band for 

cyclic life accumulated on disc assembly P/N 

LK67634 (pre RR 

SB No. RB.211–

72–5420) 

Rework band for 

cyclic life accumulated on P/Ns 

LK76036, 

UL11706, 

UL15358, 

UL22577, 

UL22578, and 

UL24738 disc assemblies (pre RR 

SB No. RB.211–

72–9434) 

–524B2–B–19 and C2–B–19, SB No. 72–7730 ........................................................ 4,000–6,000 7,000–9,000 8,500–11,000 

–524D4 series, Pre SB No. 72–7730 ........................................................................ 4,000–6,000 7,000–9,000 11,500–14,000 

–524D4–B series, SB No. 72–7730 .......................................................................... 4,000–6,000 7,000–9,000 8,500–11,000 

–524G2, G3, H, and H2 series .................................................................................. 4,000–6,000 7,000–9,000 8,500–11,000 

(1) For disc assemblies that entered into 

service before 1990, remove disc assembly 

and rework as specified in paragraph (g)(2) of 

this AD, on or before January 4, 2007, but not 

to exceed the upper cyclic limit in Table 1 

of this AD before rework. Disc assemblies 

reworked may not exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

(2) For disc assemblies that entered into 

service in 1990 or later, remove disc 

assembly within the cyclic life rework bands 

in Table 1 of this AD, or within 17 years after 

the date of the disc assembly entering into 

service, whichever is sooner, but not to 

exceed the upper cyclic limit of Table 1 of 

this AD before rework. Disc assemblies 

reworked may not exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

(3) For disc assemblies that when new, 

were modified with an application of 

anticorrosion protection and re-marked to 

P/N LK76036 (not previously machined) as 

specified by Part 1 of the original issue of RR 

service bulletin (SB) No. RB.211–72–5420, 

dated April 20, 1979, remove RB211–22B 

disc assemblies before accumulating 10,000 

cycles-in-service (CIS), and remove RB211–

524 disc assemblies before accumulating 

9,000 CIS. 

(4) If the disc assembly date of entry into 

service cannot be determined, the date of 

disc assembly manufacture may be obtained 

from RR and used instead. 

(5) Disc assemblies in RB211–535C 

operation are unaffected by the interim 

rework cyclic band limits in Table 1 of this 

AD, but must meet the calendar life 

requirements of either paragraph (f)(1) or 

(f)(2) of this AD, as applicable. 

Optional Rework of HPC Stage 3 Disc 

Assemblies 

(g) Rework HPC stage 3 disc assemblies 

that were removed in paragraph (f) of this AD 

as follows: 

(1) For disc assemblies that when new, 

were modified with an application of 

anticorrosion protection and re-marked to 

P/N LK76036 (not previously machined) as 

specified by Part 1 of the original issue of RR 

SB RB.211–72–5420, dated April 20, 1979, 

rework disc assemblies and re-mark to either 

LK76034 or LK78814 using paragraph 2.B. of 

the Accomplishment Instructions of RR SB 

No. RB.211–72–5420, Revision 4, dated 

February 29, 1980. This rework constitutes 

terminating action to the removal 

requirements in paragraph (f) of this AD. 

(2) For all other disc assemblies, rework 

using Paragraph 3.B. of the Accomplishment 

Instructions of RR SB No. RB.211–72–9434, 

Revision 4, dated January 12, 2000. This 

rework constitutes terminating action to the 

removal requirements in paragraph (f) of this 

AD. 

(3) If rework is done on disc assemblies 

that are removed before the disc assembly 

reaches the lower life of the cyclic life rework 

band in Table 1 of this AD, artificial aging 

of the disc assembly to the lower life of the 

rework band, at time of rework, is required. 

(4) Disc assemblies that entered into 

service before 1990 that have a record of 

detailed inspection are allowed to remain in 

service for 17 years from last overhaul 

inspection date but not to exceed the 

manufacturer’s published cyclic limit in the 

time limits section of the manual. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(i) Civil Aviation Authority airworthiness 

directive 004–01–94, dated January 4, 2002, 

and RR Mandatory Service Bulletin No. 

RB.211–72–9661, Revision 5, dated 

December 22, 2006, pertain to the subject of 

this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce plc Service 

Bulletin No. RB.211–72–5420, Revision 4, 

dated February 29, 1980, and Rolls-Royce plc 

Service Bulletin No. RB.211–72–9434, 

Revision 4, dated January 12, 2000, to 

perform the rework required by this AD. The 

Director of the Federal Register previously 

approved the incorporation by reference of 

these service bulletins in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51, as of 

February 24, 2004 (69 FR 2661, January 20, 

2004). You can get copies from Rolls-Royce 

plc, P.O. Box 31, Derby, England, DE248BJ; 

telephone: 011–44–1332–242424; fax: 011–

44–1332–245–418. You can review copies at 

the FAA, New England Region, Office of the 

Regional Counsel, 12 New England Executive 

Park, Burlington, MA; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. 

(k) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; telephone (781) 

238–7178; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

April 9, 2007. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7032 Filed 4–13–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30545; Amdt. No. 3214] 

Standard Instrument Approach 

Procedures, Weather Takeoff 

Minimums; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment establishes, 

amends, suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and/or Weather Takeoff 

Minimums for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, addition of 

new obstacles, or changes in air traffic 


cprice-sewell on PROD1PC66 with RULES